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NASA ACC High Energy Dynamic Impact Methodology and OutcomesFor High Energy Dynamic Impact (HEDI) events, testing to evaluate the structural response of primary aircraft structure for design and certification is both expensive and time consuming. This paper discusses current work seeking to assess, develop, and validate appropriate analytical models that accurately predict physical response, damage, and failure modes for large scale composite structures in HEDI events. Four state-of-the-art Progressive Damage Analysis (PDA) methods were employed for this phased project: LS-DYNA MAT162, LS-DYNA MAT261, Smoothed Particle Galerkin (SPG), and EMU Peridynamics. Multiple material systems were considered, namely T700/5208 textile-infusion triaxial braid, T800/AMD-825 textile-infusion triaxial braid, IM7/8552 uni-directional tape, and SPG 196-PW/8552 plain-weave fabric. Extensive ballistic impact testing was performed to support this activity and measured results were compared to predictive models for assessment using panel delamination, panel displacement, force at the load cells, and threshold velocity as measures. Ultimately, the work under this activity provided significant progress in advancing the state-of-the-art in the use of PDA for HEDI events. Each material model had favorable performance comparing to test in some parameters and needed improvement in others. With the lessons learned from this activity, significant progress was made in the ability to predict panel behavior for a more general case beyond the flat panel in a ballistic impact event. Subsequent Phase II of the NASA ACC HEDI effort will continue to build on the coupon testing, flat panel ballistic impact testing, and analysis performed to-date with application of the PDA methods for intended material selections to test articles with greater complexity of configuration, curvature, and scale. It is not the intention of this paper to present a full set of data, but rather to give an overview of the NASA HEDI effort and show a small representative subset of the test and analysis results.
Document ID
20180004407
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Hunziker, Kenneth J.
(Boeing Co. Tukwila, WA, United States)
Pang, Jenna K.
(Boeing Co. Tukwila, WA, United States)
Melis, Matthew E.
(NASA Glenn Research Center Cleveland, OH, United States)
Pereira, Joseph Michael
(NASA Glenn Research Center Cleveland, OH, United States)
Rassaian, Mostafa
(Boeing Co. Tukwila, WA, United States)
Date Acquired
August 13, 2018
Publication Date
January 8, 2018
Subject Category
Composite Materials
Report/Patent Number
GRC-E-DAA-TN50207
Meeting Information
Meeting: 2018 AIAA SciTech Forum
Location: Kissimmee, FL
Country: United States
Start Date: January 8, 2018
End Date: January 12, 2018
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NNL09AA00A
WBS: WBS 826611.04.03.01
Distribution Limits
Public
Copyright
Portions of document may include copyright protected material.
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